We=the effective weight to be used in the drop test
W=WM for main gear units (lbs.), equal to the static
reaction on the particular unit with the rotorcraft in the most critical
attitude. A rational method may be used in computing a main gear static
reaction, taking into consideration the moment arm between the main wheel
reaction and the rotorcraft center of gravity.
W=WN for nose gear units (lbs.), equal to the
vertical component of the static reaction that would exist at the nose
wheel, assuming that the mass of the rotorcraft acts at the center of
gravity and exerts a force of 1.0g downward and 0.25g
W=Wt for tailwheel units (lbs.) equal to whichever
of the following is critical --
(1) The static weight on the tailwheel with the
rotorcraft resting on all wheels; or
(2) The vertical component of the ground reaction that would occur at
the tailwheel assuming that the mass of the rotorcraft acts at the center
of gravity and exerts a force of 1g downward with the rotorcraft in
the maximum nose-up attitude considered in the nose-up landing conditions.
h=specified free drop height (inches).
L=ratio of assumed rotor lift to the rotorcraft weight.
d=deflection under impact of the tire (at the proper inflation
pressure) plus the vertical component of the axle travel (inches) relative
to the drop mass.
n=limit inertia load factor.
nj=the load factor developed, during impact, on the
mass used in the drop test (i.e., the acceleration dv/dt in g'
s recorded in the drop test plus 1.0).